# Initialize B-2 Spirit plane object
plane = Plane(1420000, 52.4, 9.1, 0.0090, 0.92, 1.22)
# Generate data at requested altitudes
altitudes = []
speed_const_Cl = []
speed_stall = []
drag_const_Cl = []
drag_210 = []
for i in range(0, 20001, 500):
plane.set_altitude(i)
altitudes.append(i)
density = atm.density_at(i)
speed_stall.append(plane.speed_stall())
speed = plane.speed(plane.Cl_min_drag)
speed_const_Cl.append(speed)
Cd_min = plane.Cd(plane.Cd_i(plane.Cl_min_drag))
drag_const_Cl.append(plane.drag(Cd_min, speed))
speed = 210 # m/s
Cd = plane.Cd(plane.Cd_i(plane.Cl(speed)))
drag_210.append(plane.drag(Cd, speed))
# Reformat as Strings
alt_str = ['%d' % i for i in altitudes]
v_const_Cl_str = ['%.1f' % i for i in speed_const_Cl]
d_const_Cl_str = ['%.2f' % (i / 1000.0) for i in drag_const_Cl]
d_210_str = ['%.2f' % (i / 1000.0) for i in drag_210]
T_a_Drag_min_Ratios = []
for i in range(0, 20001, 500):
altitudes.append(i)
density = atm.density_at(i)
speed = plane.speed(plane.Cl_min_drag)
Cd_min = plane.Cd(plane.Cd_i(plane.Cl_min_drag))
drag_min = plane.drag(Cd_min, speed)
thrust_avail = plane.jet_thrust_available()
thrust_drag_ratio = thrust_avail / drag_min
T_a_Drag_min_Ratios.append(thrust_drag_ratio)
speed_stall = plane.speed_stall()
Cl_stall = plane.Cl(speed_stall)
Cd_stall = plane.Cd(plane.Cd_i(Cl_stall))
stall_drags.append(plane.drag(Cd_stall, speed_stall))
plt.cla()
plt.clf()
plt.plot(altitudes, T_a_Drag_min_Ratios)
plt.title('T_a/D_min Ratio vs. Altitude')
plt.xlabel('Altitude [m]')
plt.ylabel('T_a/D_min Ratio')
plt.show()
"""QUESTION 5"""
plt.cla()
plt.clf()
plt.plot(altitudes, stall_drags)